Burner and method for reducing combustion humming during operation

• US 6,374,593 B1
• Filed: 09/20/2000
• Issued: 04/23/2002
• Est. Priority Date: 03/20/1998
• Status: Expired due to Fees

• Current Assignee: Siemens AG
• Original Assignee: Siemens AG
• Inventors: Ziegner, Manfred
• Primary Examiner(s): Freay, Charles G.
• Assistant Examiner(s): Gartenberg, Ehud
• Application Number:
  US09/646,612
• Time in Patent Office: 580 Days
• Field of Search: 607/48, 607/46, 607/37, 60/390.2
• US Class Current: 60/772
• CPC Class Codes: F23C 7/004 using vanes
• CPC Class Codes: F23D 2206/10 Turbines
• CPC Class Codes: F23D 2210/00 Noise abatement
• CPC Class Codes: F23D 23/00 Assemblies of two or more burners gas burners with provision for a retention flame F23D14/26

Abstract

Combustion air or a combustion air/fuel mixture is supplied in a flow to a combustion process of a burner. A swirl, which is non-uniform in the peripheral direction, is imposed on the flow. A flow duct, in which is arranged a swirl device for imposing the swirl, is used for the supply of the combustion air or the combustion air/fuel mixture. As such, combustion oxcillations are reduced.

Claims

1. A gas turbine burner, comprising:

a flow duct, configured as an annular duct, adapted to guide a flow of one of combustion air and a combustion air/fuel mixture wherein the flow duct includes a swirl device for imposing a swirl on the flow, the swirl device being configured for the imposition of a swirl, which is non-uniform around the periphery of the annular duct, on the flow.

2. The gas turbine burner of claim 1, wherein each of a number of swirl elements of the swirl device includes a deflection surface with an outlet angle (α

) relative to the main flow direction at its outlet end, the outlet angles (α

) of at least two directly adjacent swirl elements being different.

3. The gas turbine burner as claimed in claim 2, wherein each swirl element is configured as a swirl vane.

4. The burner as claimed in claim 2, wherein the swirl device is formed from a plurality of swirl groups, each swirl group having a plurality of swirl elements with the same outlet angles (α

₁),(α

₂), the swirl elements of adjacent swirl groups having different outlet angles (α

₁, α

₂).

5. The gas turbine burner as claimed in claim 1, wherein the gas turbine burner is embodied as a hybrid burner.

8. The burner as claimed in claim 3, wherein the swirl device is formed from a plurality of swirl groups, each swirl group having a plurality of swirl elements with the same outlet angles (α

₁),(α

₂), the swirl elements having different outlet angles (α

₁, α

₂).

9. The gas turbine burner as claimed in claim 2, wherein the gas turbine burner is embodied as a hybrid burner.

10. The gas turbine burner as claimed in claim 3, wherein the gas turbine burner is embodied as a hybrid burner.

11. The gas turbine burner as claimed in claim 4, wherein the gas turbine burner is embodied as a hybrid burner.

6. A method of reducing combustion oscillations during the operation of a gas turbine burner with a flow duct, configured as an annular duct, comprising:

imposing a swirl, which is non-uniform around the periphery of the annular duct, on a flow, in the annular duct, of one of a combustion air/fuel mixture and of combustion air; and

supplying the flow to a combustion process.

7. The method as claimed in claim 6, further comprising:

feeding the fuel into the annular duct, by means of a fuel inlet, upstream of an outlet end of a swirl device arranged in the annular duct.